Fluid supercharging device

ABSTRACT

A fluid supercharging device, comprising: a rotating shaft; a vane disc coaxially fixed to the rotating shaft; a plurality of fan blades fixed around a perimeter of the vane disc; the back side of the fan blades being provided with at least one fluid guiding inlet, an end of the back side distal from the vane disc is provided with a fluid guiding outlet, a fluid channel communicating the fluid guiding inlet with the fluid guiding outlet is provided along a lengthwise direction inside the fan blades; the fan blades rotate to generate a centrifugal force such that a fluid flows into the fluid channel via the fluid guiding inlet on the back side, and flows out of the fluid guiding outlet along the lengthwise direction of the fan blades.

CROSS-REFERENCE TO RELATED APPLICATIONS

The present application is a divisional application of U.S. patentapplication Ser. No. 14/456,385, filed on Aug. 11, 2014, now pending,which is a continuation-in-part of International Patent Application No.PCT/CN2013/071260, filed on Feb. 1, 2013, now pending, which itselfclaims priority to Chinese Patent Application No. CN201210030149.5,filed on Feb. 10, 2012, which are hereby incorporated by reference intheir entireties.

TECHNICAL FIELD

The present invention relates to a power device, and in particular, to afluid supercharging device and a turbine engine using the superchargingdevice.

BACKGROUND

The widely used turbine engine, for example, the turbine engine used inaircrafts, generally employs a compressor and a turbine having amulti-stage structure to increase the internal pressure within theengine, and implements combustion in cooperation with a combustionchamber, thereby jetting high-pressure fluid and generating a propellingforce to push the aircraft to fly. At present, the pressure generated bythe compressor and the turbine that operate under action of a drivingforce is not great, and the fuel fails to be fully combusted within thecombustion chamber of the engine. Therefore, the generated propellingforce is not great either. Accordingly, an improvement is desired.

SUMMARY

One objective of embodiments of the present invention is to provide afluid supercharging device, comprising: a rotating shaft for rotatingunder action of a driving force; a vane disc coaxially fixed to therotating shaft; a plurality of fan blades fixed around a perimeter ofthe vane disc; wherein: at least one of the fan blades employs asupercharging structure where a leeward side of the at least one of thefan blades is provided with at least one fluid guiding inlet, an end ofthe leeward side distal from the vane disc is provided with a fluidguiding outlet, a fluid channel communicating the fluid guiding inletwith the fluid guiding outlet is provided along a lengthwise directioninside the fan blades; the fan blades rotate to generate a centrifugalforce such that a fluid flows into the fluid channel via the fluidguiding inlet on the leeward side, and flows out of the fluid guidingoutlet along the lengthwise direction of the fan blades, the fluid flowsalong different paths between a windward side and the leeward side ofthe fan blades in different flow velocities to generate a pressuredifference.

Another objective of embodiments of the present invention is to provideanother fluid supercharging device, comprising: a rotating shaft forrotating under a driving force; a vane disc coaxially fixed to therotating shaft; a plurality of fan blades fixed around a perimeter ofthe vane disc; wherein: at least one of the fan blades employs asupercharging structure where a leeward side of the at least one of thefan blades is provided with at least one fluid guiding inlet, and afluid channel in communication with the fluid guiding inlet is providedalong a lengthwise direction inside the fan blades; the superchargingdevice further comprising a suction motor, wherein a gas intake of thesuction motor is in communication with the fluid channel and operable toextract gas stream under action of a driving force, such that a fluidflows into the fluid channel via the fluid guiding inlet on the leewardside and generates an accelerated flow velocity within the fluidchannel.

Still another objective of embodiments of the present invention is toprovide A turbine engine, comprising: a housing, the housing being of ahollow cylindrical shape, a front portion of the housing being providedwith a gas intake passage, a rear portion thereof being provided with ajetting port, an inner portion thereof being provided with a combustionchamber; a compressor and a turbine that are formed by a multi-stagevane disc and a plurality of fan blades being coaxially coupled to arotating shaft, the plurality of fan blades being fixed around aperimeter of the vane disc; wherein: at least one of the fan bladesemploys a supercharging structure where a leeward side of the at leastone of the fan blades is provided with at least one fluid guiding inlet,and a fluid channel in communication with the fluid guiding inlet and afluid guiding outlet is provided along a lengthwise direction inside thefan blades; the supercharging device further comprising a suction motor,wherein a gas intake of the suction motor is in communication with thefluid guiding outlet of the fluid channel and operable to extract gasstream under action of a driving force, such that a fluid flows into thefluid channel via the fluid guiding inlet on the leeward side andgenerates an accelerated flow velocity within the fluid channel.

Yet still another objective of embodiments of the present invention isto provide an engine, comprising: a housing, the housing being of ahollow cylindrical shape, a front portion of the housing being providedwith a gas intake passage, a rear portion thereof being provided with ajetting port, an inner portion thereof being provided with a combustionchamber; a compressor and/or a turbine being provided coaxially with arotating shaft and received in the housing; wherein: a rear portion ofthe compressor is provided, coaxially with the rotating shaft, with ahollow rotating cylinder with a higher rotation velocity, the hollowrotating cylinder being received in the combustion chamber, such thatfuel in the combustion chamber is fully combusted with extension of afluid flowing path as the hollow rotating cylinder rotates.

The embodiments of the present invention achieve the followingbeneficial effects: When the fan blades of the supercharging device ofthe engine rotates at a high velocity, a great centrifugal force isgenerated, which throws the fluid at the center to the surrounding. Whenthe fluid flows around to the leeward side of the fan blades from thewindward side of the fan blades along the outer shape, the fluid easilyenters the fluid channel via the fluid guiding inlet. Under action ofthe centrifugal force, the fluid quickly passes through the fluidchannel, and flows, through a guiding fluid at an end portion of the fanblades, out of the fluid guiding outlet and jetted backward, which isconsistent with the direction of discharging fluid by the turbineengine, and collaboratively generates an even greater pushing force. Inaddition, two high-velocity fluid layers are formed. One is formed onthe leeward side of the fan blades, and the other is formed inside thefluid channel, which form a pressure difference with the fluid layer onthe fluid layer on the windward side of the of the fan blades due todifferent flow velocities. The pressure difference transfers from thewindward side of the fan blades to the leeward side of the fan blades,thereby further increasing the pressure within the engine and generatingan even greater propelling force.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a schematic structural diagram of a supercharging device for aturbine engine according to an embodiment of the present invention;

FIG. 2 is an A-A sectional view of the supercharging device in FIG. 1;

FIG. 3 is a schematic sectional view taken at the same position as theA-A position in FIG. 2 according to another embodiment of the presentinvention;

FIG. 4 is a schematic structural diagram of another supercharging devicefor a turbine engine according to an embodiment of the presentinvention;

FIG. 5 is a schematic structural diagram of still another superchargingdevice for a turbine engine according to an embodiment of the presentinvention;

FIG. 6 is a schematic structural diagram of yet still anothersupercharging device for a turbine engine according to an embodiment ofthe present invention; and

FIG. 7 is a schematic structural diagram of a hollow device in acombustion chamber of a turbine engine according to an embodiment of thepresent invention.

DENOTATIONS OF REFERENCE SIGNS

1—housing; 2—front gas intake passage; 3—compressor; 4—combustionchamber; 5—jetting port; 7—suction motor; 9—spoiler face;

101—front cylinder; 102—rear cylinder;

301—fan blade; 302—windward side; 303—leeward side; 304—fluid channel;305—fluid guiding inlet; 306, 307—fluid guiding outlet; 308—vane disc;309—central line;

401—nozzle;

601—front cylinder jetting port; 602—rear cylinder jetting port;

701—rotating shaft outer cover; 702—hollow rotating cylinder; 703—hollowrotating conical cylinder;

801—suction pipe; 802—rotating shaft inner channel; 803—gas outtake;804—bearing structure;

902—double-layered channel; 903—lower-layer channel; 904—guiding fluid;905—suction port.

DETAILED DESCRIPTION Embodiment 1

With reference to FIG. 1 and FIG. 2, an embodiment of the presentinvention provides a fluid supercharging device for a turbine engine.The supercharging device comprises: a housing 1, a compressor 3, acombustion chamber 4, and a turbine 5. The compressor 3 and the turbine5 both comprise a rotating shaft 7. An impeller structure is formed by avane disc 308 and a plurality of fan blades 301 arranged around aperimeter thereof In the embodiment of the present invention, the sideof the fan blades 301 facing toward the fluid is a front side 302 (i.e.,a windward side 302) and the side of the fan blades 301 backing on tothe fluid is a back side 303 (i.e., a leeward side 303). For descriptionbrevity, unless otherwise specified, the impeller hereinafter refers tothe vane disc. The rotating shaft 7 is operable to rotate under actionof a driving force, the vane disc 308 is coaxially fixed to the rotatingshaft 7, and the fan blades 301 are fixed to the perimeter of the vandisc 308. For description brevity, unless otherwise specified, asupercharging structure of the compressor is also the superchargingstructure of the turbine. At least one of the compressor 3 and theturbine 5 employs a structure of the fluid supercharging deviceaccording to the present invention. For example, in this embodiment, anexample is given where: at least one fluid guiding inlet 305 is arrangedalong a lengthwise direction of leeward side housing of at least one ofthe fan blades 301, and a fluid guiding outlet 306, 307 is arranged onan end portion along of the lengthwise direction of the leeward sidehousing, i.e., an end portion distal from the vane disc 308, a fluidchannel 304 communicating the fluid guiding inlet 305 with the fluidguiding outlet 306, 307 is provided along a lengthwise direction insidethe fan blades, such that a fluid flows into the fluid channel via thefluid guiding inlet on the leeward side and length wisely passes thoughthe fan blades to an end portion of the fan blades, and flows out of thefluid guiding outlet. It is preferable that a plurality of fluid guidinginlets 305 are arranged on an entire length, such that an even greaterpressure difference is formed between the windward side and the leewardside. It is preferable that the space of the fluid channel 304 is aslarge as possible, such that more fluid on the leeward side flowsthrough at a high velocity in the fluid channel under action of acentrifugal force, and generates an even greater pressure difference.

The housing 1 is of a hollow cylindrical shape, a front portion of thehousing 1 is provided with a gas intake passage 2, and a rear portionthereof is provided with a jetting port 6. The combustion chamber 4 isformed by enclosure with inner space of the housing 1, and an inner wallof the housing 1 is provided with a nozzle 401 for jetting fuel. Thecompressor 3 and the turbine 5 are coaxially arranged, and received inthe housing 1. A leeward side 303 of the compressor faces toward thejetting port 6 of the housing, a windward side of the turbine 5 facestoward the leeward side 303 of the compressor. To be specific, in thedirection from the gas intake passage 2 to the jetting port 6, thecompressor 3 and the turbine 5 are sequentially arranged along therotating shaft 7. In an embodiment, the compressor 3 and/or the turbine5 is of a multi-stage vane disc structure. Stages of vane discs aresequentially arranged coaxially, and the fan blades 301 fixed on eachstage of vane disc 308 all employ the supercharging structure.

In this embodiment, the leeward side of the fan blades 301 is providedwith a plurality of fluid guiding inlets 305 what are arranged along thelengthwise direction of the fan blades 301. The fluid guiding inlet 305may be of a circle shape, an elongated shape, a rhombus shape, anellipse shape, or an arc shape. In an embodiment, a central line of anopening-shape central line of the fluid guiding inlet 305 is consistentwith rotation direction and angle of the fan blades 301, such that thefluid successfully enters the guiding inlet when the fan blades rotate.Further, the number and size of the fluid guiding inlets 305 decreaseprogressively along a direction distal from the vane disc 308, such thatthe fluid is guided into the fluid channel 304.

In this embodiment, the turbine engine and the supercharging deviceoperate as follows: When the fan blades of the engine rotate at a highvelocity, a greater centrifugal force is generated which pushes thecentral fluid all around; when the fluid flows from the windward side302 of the fan blades 301 along the external shape thereof to theleeward side 303 of the fan blades 301, the fluid may easily enter thefluid channel 304 (especially when the central line of the opening-shapecentral line of the fluid guiding inlet 305 is consistent with rotationdirection and angle of the fan blades 301, the fluid may more easilyenter the guiding inlet). Under action of the centrifugal force, thefluid quickly passes through the fluid channel 304, and flows, throughan arc-shape guiding fluid at an end portion of the fan blades, out ofthe fluid guiding outlet 306, 307 and jetted backward, which isconsistent with the direction of discharging fluid by the turbineengine, and collaboratively generates an even greater propelling force.In addition, the housing of the leeward side 303 of the fan blades 301and the fluid channel 304 collaboratively form a fluid layer with innerand outer layers having a high motion velocity, which generates apressure difference with a fluid layer on the windward side 302 of thefan blades 301 due to different flow velocities. If each stage of fanblade 301 of the compressor 3 employs such supercharging structure, thewindward side 302 and the leeward side 301 of each stage of fan blade301 generate a pressure difference therebetween. The pressure differencetransfers stage-by-stage from the windward side 302 of the fan blades301 to the leeward side 301 of the fan blades 301 to the combustionchamber 4. The pressure difference is a source of the propelling force,the pressure difference generated by the multiple stages of fan bladescauses the pressure within the engine to increase, and thus thepropelling force is increased. Meanwhile, stages of fan blades 301 ofthe compressor 3 also suction the fluid from the gas intake passage 2,and after compression, the compressor 3 discharges high-pressure fluidto enter the combustion chamber 4, the high-pressure fluid blends andcombusts with the fuel jetted from the nozzle 401 in the combustionchamber 4, and the fluid is then suction by the multiple stages of fanblades due to the pressure difference generated by the superchargingdevice of the turbine 5, and re-compressed, and high-pressure andhigh-temperature glowing fluid is jetted from the jetting port 6 at ahigh velocity. This greatly improves the propelling force of anaircraft. The fluid channel in the multiple stages of fan blades in theturbine enlarges the combustion space in the combustion chamber, enablesufficient combustion of the fuel.

Generally the length of the fan blades 301 is greater than that thewidth thereof. Therefore, the path where the fluid flows through thefluid guiding inlet 305, the fluid channel 304, and the fluid guidingoutlet 306, 307, is much larger than the path where the fluid flowsthrough the width of the fan blade. Meanwhile, the direction along whichthe fluid flows through the fluid channel 304 is consistent with thecentrifugal force. Therefore, under action of a traction force generatedby the centrifugal force, the flow velocity of the fluid is sharply andinstantly increased on the leeward side of the fan blades, whichgenerate a pressure difference from the windward side of the fan bladesdue to different flow velocities. In this case, stages of fan blades 301all stage-by-stage transfer backward the pressure differences thereof indescending order. This generates a great flow pressure within theengine. However, a traditional engine generates no fluid pressuredifference, but only generates a propelling force after suctioningfluid, compressing the fluid, and then discharging the fluid. Accordingto the present invention, the pressure difference, as another source ofthe propelling force, is proposed, which generates an even greaterpropelling force collaboratively with the fluid suction by the fanblades and then compressed.

According to the embodiment of the present invention, under action ofthe great propelling force, the fluid on the leeward side of the fanblades is changed from flowing through the widthwise direction to thelengthwise direction (flowing through the fluid guiding channel). Inthis way, the flow velocity of the fluid is increased, and a fluidpressure difference is generated, such that the pressure within theengine is improved. Therefore, the fluid jetted from the nozzle of theengine generates a propelling force greater than that generated by atraditional engine.

In the supercharging device according to the present invention, thewindward side 302 and the leeward side 303 of the fan blades of eachstage of vane disc 308 are subject to a pressure difference, and theplurality of fluid guiding inlets 305 arranged on the leeward side ofeach of the fan blades 301 are in communication with the fluid channel304, achieving layer-by-layer coverage like bird's feather. Therefore,as fluid will not depart from the feather, the fluid will not departfrom the housing of the fan blades 301, and the fluid pressure differentis always present between the leeward and windward sides of the fanblades 301. This effectively prevents the surge phenomenon due toreverse expansion of high-pressure air at the rear portion, and greatlyimproves safety of the aircraft.

In another embodiment, the vane disc 308 of the compressor 3 and theturbine 5 of the supercharging device may be designed to one stage ormultiple stages according to actual requirements. The number, size, andshape of fluid guiding inlets 305 on the leeward side 303 of each stageof fan blade 301 affect the volume and velocity of the fluid flowingthrough the surface thereof, and thus affect the pressure differencegenerated between the windward side 302 and the leeward side 303.Generally, different stages of vane discs of the conventional engine aredriven at different velocities, i.e., coaxial but non-concentric.Therefore, the manufacture process is very complicated, and the safetyand stability are poor. In the present invention, the pressuredifference between different stages of fan blades may be controlled byarranging the fluid guiding inlets 305 of different quantities andshapes on different stages of fan blades 301, which is simpler, moreconvenient, suitable and safe over the conventional engine.

In another embodiment, the supercharging device may be provided for onlythe fan blades fixed on the last stage of vane disc distal from a gasintake direction, such that the low flow velocity and high gas pressureof the prior multiple stages of fan blades and the high flow velocityand low gas pressure of the last stage of fan blade form a fluidpressure difference therebetween, and thus collaboratively form an evenlarger forward-to-backward pressure difference transfer area. In thisway, the engine generates an even greater propelling force.

In another embodiment, the compressor or turbine using the fan blades ofat least one stage of vane disc of the fluid supercharging device, underdriving of power, may also achieve a better supercharging effect, andgenerating a greater propelling force.

Further, as illustrated in FIG. 2, the fan blades of the stage of vanedisc at the rear of the compressor or the turbine housing 1, and underdriving of power, the supercharging device may also achieve a bettersupercharging effect, and generating a greater propelling force.

Further, the fluid supercharging device is also applicable to a powerdevice in the water. For example, in the water, the fan blades aroundthe perimeter of on stage of vane disc driven by the power device in thewater, from the guiding inlet and the guiding outlet on the downstreamface, are in communication with the inner fluid channel, such that underaction of the centrifugal force, a propelling force is generated due toa pressure difference caused by different flow velocities between theupstream face and the downstream face. Further in cooperation with theoriginal propelling force generated by suctioning and discharging waterby the fan blades, an even greater propelling force is generated.

Further, as illustrated in FIG. 2, the vane disc 308 and the pluralityof fan blades 301 arranged around the perimeter thereof, under drivingof an external force, cause a further pressure difference to thesupercharging device between inner and outer surfaces during rotation ofthe fan blades, wherein the external power comprises a wind force, ahydraulic force, a stream force, and a driving force capable of drivingthe fan blades to rotate. The pressure difference herein is a source ofthe propelling force. In this way, the fan blades rotate more quickly,which drives the vane disc 308. The vane disc drives the rotating shaft7 coupled thereto to rotate more quickly. The rotating shaft 7 drivesthe power generator (not illustrated in the drawing) to generate moreelectricity.

Embodiment 2

FIG. 3 and FIG. 4 illustrate a turbine engine according to anotherembodiment of the present invention. In this embodiment, a suction motor8 is only in communication with the fluid channel 304 within the fanblades of the compressor via a suction pipe 801 and a rotating shaftinner channel 802. Different from Embodiment 1, the fluid guiding outlet306, 307 are closed, and the fluid entering the fluid channel 304 viathe fluid guiding inlet 305 does not flow out from the fluid guidingoutlet at an end portion of the fan blades but is extracted out by thesuction motor 8. A suction port 905 of the suction motor 8 is incommunication with the fluid channel 304, and is operable to extract thegas flow out under action of a driving force. The extremely greatsuction force enables the fluid to enter the fluid channel 304 at a highvelocity from the plurality of fluid guiding inlets 305 on the leewardside of the fan blades, and increases the flow velocity within the fluidchannel and the leeward side of the fan blades. The suction pipe 801 ofthe suction motor 8 is in communication to the channel 802 within thehollow rotating shaft 7 (for example, the suction pipe 801 iscommunicated to the rotating shaft inner channel 802 via a bearingstructure 804), and thus is in communication with the fluid channel 304and the plurality of fluid guiding inlets 305 on the leeward side of thefan blades 301.

In this embodiment, structures of the plurality of fluid guiding inletsand the multiple stages of fan blades similar to those in Embodiment 1may also be used, which are thus not described herein any further.

In an embodiment, the suction motor 8 may be in communication with thefluid channel 304 using the following structure. As illustrated in theright part in FIG. 3, the suction motor may further comprise the suctionpipe 801, wherein the suction port 905 of the suction pipe 801 ispositioned at a top end where the fan blades 301 are distal from thevane disc 308 in the fluid channel, and is communication with the fluidguiding inlet 305 on the leeward side of the fan blades and the fluidchannel 304 therein. The suction pipe 801 extends along a lengthwisedirection of the fan blades 301 and is in communication with therotating shaft inner channel 802, and further in communication with agas intake of the suction motor 8. When the vane disc of the compressor3 and the suction motor 8 simultaneously operate, the suction motor 8generates a suction force to enable the fluid in the fluid guiding inlet305 and the fluid channel 304 arrives at the end portion of the fanblades, is then suction into the suction pipe 801 via the suction port905, and finally arrives to a gas outtake 803 via the rotating shaftinner channel 802. In this case, preferably the fluid discharged fromthe gas outlet 803 discharged into the gas intake passage 2 via apipeline and thus reenters the engine (not illustrated in the drawing).Alternatively, according to the actual situation, if the suction volumeis not great, a part of the fluid may be discharged outside from the gasouttake 803. In this case, the path along which the fluid on the leewardside of the fan blades flows is almost doubled, thereby forming threehigh-velocity fluid layers that are isolated from each other but incommunication with each other. One layer is formed within the suctionpipe, one layer is formed on the leeward side 303 of the fan blades 301,and the other layer is formed within the fluid channel 304. Similar tothe analysis in Embodiment 1, due to the centrifugal force anddifference of lengths of the paths along which the fluid flows, thesehigh-velocity fluid layers generates a great flow velocity with the lowvelocity layer on the windward side, thereby generating an even greaterpressure difference. In this way, the fluid pressure forward-to-backwardtransfers, generating an even greater propelling force.

In an embodiment, the suction motor 8 is arranged outside the turbineengine, and the suction port 803 thereof discharges the fluid extractedvia the suction pipe 801 to the outside of the engine. With respect touse of an external suction motor, different models may be selectedaccording to actual requirements. The power of the suction motor 8 maybe increased to achieve a better suction effect.

In another embodiment, the suction pipe 801 may also employ a threadedpipe or a spiral pipe, to further enlarge the path along which the fluidflows, and improve the flow velocity. Similar to Embodiment 1, in thisembodiment, the surface of the fan blades may not be subject to thedrop-off phenomenon either.

In addition, by control of the suction motor, the present invention onlyconsumes small energy of the suction motor and increases the flowvelocity of the small-volume fluid within the fluid channel. Obviously,it may be easily ensured that the flow velocity on the leeward side ofthe fan blades is several times higher than that on the windward side.This generates a tens of times of fluid pressure difference between thefront and rear surfaces of the fan blades. The pressure differencecauses a propelling force, thereby causing the propelling force of theengine to improve drastically. Therefore, the number of stages of thevane disc within the engine may be correspondingly reduced;alternatively the suction motor is only in communication with the fluidchannel within the last stage of vane disc of the compressor 3, whichalso cause greatly improves the propelling force of the engine.

In this embodiment, the flow velocity on the leeward side of the fanblades is increased by extracting air by the suction motor. This furtherincreases the fluid pressure, and provides basis for innovativedevelopment of various engines having a greater propelling force.

Embodiment 3

In another embodiment of the turbine engine of the present invention,the combustion chamber 4 may not be set. The suction pipe 801 of thesuction motor 8 is in communication with the fluid channel of at leastone stage of fan blades of the compressor 3 and the turbine 5. Thedesign may follow the structure design in the above embodiments. Apropelling force is generated by the pressure difference caused due todifferent flow velocities on the front and rear surfaces of the fanblades. This propelling force, together with the propelling forcegenerated by the fan blades by suction and compressor air, enables asufficient propelling force for the engine even without the combustionchamber 4. The pressure difference generated by the turbine shall notexceed that generated by the compressor, such that the fluid pressuretransfers from a high level to a low level.

Embodiment 4

FIG. 3 and FIG. 5 illustrate a supercharging device of a turbine engineaccording to another embodiment of the present invention. In thisembodiment, the suction motor 8 may be in communication with the fluidchannel 304 using the following structure. As illustrated in the leftpart in FIG. 3, the fluid channel 304 is internally partitioned into tochannels, i.e., a first channel 902 in communication with the fluidguiding inlet 305 and a second channel 903 in communication with the gasintake 905 of the suction motor 8. The first channel 902 is incommunication with the second channel 903 at the end of the fan blades301 distal from the vane disc 308. In an embodiment, an inner wall ofthe fluid channel 304 and/or a surface of the isolation layer is aspoiler face 9 along a long fluid flowing path, wherein the spoiler face9 may be a concave-convex streamline shape, a wave shape, or a pluralityof repeatedly arranged arc shapes. The first channel 902 and the secondchannel 903 may be upper and lower channels, or left and right channels,or two channels diagonally arranged within the fluid channel.

In an embodiment, the suction motor 8 may be disposed inside the turbineengine. As illustrated in FIG. 5, the suction motor 8 is coaxiallyarranged with the rotating shaft 7 of the engine but has a differentrotation velocity from the engine. The rotation velocity of the suctionmotor 8 is greater than that of the rotating shaft. Specifically, thesuction motor 8 may be disposed within a rotating shaft outer cover 701at an end portion of the rotating shaft of the compressor, the suctionmotor is in communication with the fluid channel 304 within the fanblades 301 and within the rotating shaft inner channel 802 of the hollowrotating shaft 7 via the suction pipe 801, and discharges the suctionedfluid into the engine via the gas outtake 803.

Embodiment 5

FIG. 6 illustrates a turbine engine according to another embodiment ofthe present invention. Different from the above embodiments, in thisembodiment, the housing 1 comprises a front cylinder 101 and a rearcylinder 102 that are sequentially arranged along an axial direction,wherein a diameter of the front cylinder 101 is greater than that of therear cylinder 102; the jetting port of the housing 1 comprises a rearjetting port 602 and an annular front jetting port 601 formed at aboundary of the front cylinder 101 and the rear cylinder 102; and thecompressor 3 is received in the front cylinder 101 and the turbine 5 isreceived in the rear cylinder 101.

Stages of fan blades may employ the supercharging manner described inthe above embodiments. For example, the suction pipe 801 is arranged inthe fluid channel 304. According to the manner illustrated in FIG. 4,the suction pipe 801 is in communication with the external suction motor8 via the rotating shaft inner channel 802 of the hollow rotating shaft7.

When the engine and the motor simultaneously operate, the suction motorgenerates a great suction force, and under cooperation of thecentrifugal force, suctions at a high velocity the fluid from the fluidguiding inlets 305 into the fluid channel 304, such that the fan bladeswithin the front cylinder form a pressure difference due to differentflow velocities. The high-pressure fluid discharged by the frontcylinder is partitioned into two parts, wherein one part is jetted fromthe annular front jetting port 601 and the other part is suctioned bythe turbine within the rear cylinder 102 and fully blends and combustswith the fuel in the combustion chamber 4. Finally, the high-velocityglowing fluid is jetted from the rear cylinder jetting port 602. Thefluids jetted from the front cylinder jetting port 601 and the rearcylinder jetting port 602 pushes the aircraft to fly.

In an embodiment, in the multiple stages of fan blades in the frontcylinder, the fluid guiding inlets may be only arranged on the laststage of fan blade, such that the prior stages of fan blades generate ahigh pressure due to low flow velocity, and transfers the pressuredifference to low pressure generated by high flow velocity on the backsurface of the last stage of fan blade, to generate an even greaterpropelling force.

In another embodiment, the suction motor 8 may not be employed, whereasthe supercharging manner according to Embodiment 1 may be employed, thatis, a fluid guiding outlet is arranged at an end portion of the fanblades. In this way, a pressure difference may be obtained, and inaddition the area of the combustion chamber is enlarged, combustionefficiency is improved, and an even greater propelling force isgenerated, since the stages of fan blades of the turbine 5 have guidinginlets and guiding outlets in communication with the inner fluidchannel.

In another embodiment, the combustion chamber may not be employed.Similar to Embodiment 3, a propelling force is generated by a pressuredifference generated by the fan blades in the front and rear cylindersand a pressure generated by the fan blades by suctioning and compressingair.

In addition, according to the embodiment of the present invention, thesupercharging device may also be applied to other types of engines, forexample, a ramjet engine. The supercharging device according to theembodiment of the present invention is arranged in the ramjet engine, togenerate a great fluid pressure, which enables the combustion chamber ofthe ramjet engine to generate high temperature and high pressure under avery high fluid pressure, thereby generating an even greater propellingforce.

The present invention is an improvement and development of theconventional aircraft engine, and provides a novel, practical andfeasible way for development of an engine with an even greaterpropelling force.

Embodiment 6

In the above embodiments, the fluid channel in the multiple stages offan blades in the turbine enlarges the combustion space in thecombustion chamber, enable sufficient combustion of the fuel. Referringto FIG. 7, different from the above embodiments, two arc-shape spoilersare arranged on the coaxial but non-concentric (conventional techniquein the art) rotating shaft 7, the spoilers are left-to-rightsymmetrically coupled to the rotating shaft 7, thus forming a hollowrotating cylinder 702, which is arranged at a rear portion of thecompressor 3 and received in the combustion chamber 4. A spiralstructure on the outer surface of the two spoilers causes the hollowrotating cylinder to form a spiral shape during rotation. Therefore,when the fuel jetted by the nozzle 401 is combusted in the combustionchamber, since the hollow rotating cylinder 702 is very light, the loadduring the rotation is far less than that of the compressor, and thusthe rotation velocity is very high. When rotating at a high velocity,the two arc-shape spoilers form an arc-shape body with the outer surfacebeing of a spiral shape, and additionally a great centrifugal force isgenerated which throws the combusting fluid instantly from the center toall around. In this way, a hollow state is formed at the center of thehollow rotating cylinder. This state is favorable to combustion of thefuel around the rotating cylinder. Meanwhile, the spiral shape formed onthe outer surface of the hollow rotating cylinder enables the combustingfluid to flow through circularly and repeatedly along an extended spiralpath. During this high-velocity rotation, the long spiral-shape path andspace which the high-temperature and high-pressure combusting fluid flowthrough enables sufficient combustion of the fuel. Obviously, the spiralpath around the hollow rotating cylinder is several times longer thanthe path which the fluid in the combustion chamber 4 directly flowsthough. Even it is simple to increase the path by tens of times toenable sufficient combustion of the fuel. In other words, the combustionarea of the combustion chamber is increased by tens of times. Only whenthe fuel is combusted sufficiently, the engine can obtain a greaterpropelling force.

According to the present invention, the space of the combustion chamber4 of the engine is not yet enlarged; instead, an arc-shape spiral bodyis formed during the coaxial but non-concentric high-velocity rotationof the hollow rotating cylinder 702 arranged in the combustion chamberwith the rotating shaft 7. During the high-velocity rotation of thehollow rotating cylinder, the fuel is sufficiently combusted by means ofspace and time obtained when the fuel flows through the extended path.

In this case, a hollow rotating conical cylinder 703 may also bearranged at the rear of the turbine 5. The hollow rotating conicalcylinder 703 forms a triangle with two straight-line spoilers. The apexof the triangle extends from the cross-section of the jetting port 6 tothe outside for a specific distance. When the triangle rotates at a highvelocity, a cone is formed. The combusting fluid flows through thecombustion chamber and the turbine, and then circularly flows throughthe spiral shape on the outer surface of the conical body repeatedly andconcentrates at the cone tip of the con, i.e., the center of thecross-section of the jetting port 6 extending outside for a specificdistance. In this way, the extension distance of the jetting port 6 tothe outside is increased. In this state, the fluid flowing through thejetting port 6 concentrates at the central cone tip. That is, as thevolume and temperature of the concentrated fluid at the center portionof the jetting port 6 are both greater than those of the surrounding,the fluid is jetted at a high velocity, thereby generating an evengreater propelling force. The hollow rotating cone cylinder 703 rotatesto form the cone tip of the cone, which may be also arranged within thejetting port 6.

The hollow rotating cylinder 702 and the hollow rotating conicalcylinder 703 are all formed by two spoilers, or may be formed by morethan two spoilers. A spiral shape is formed on the outer surface of thespoiler, and the hollow rotating cylinder 702 and the hollow rotatingconical cylinder 703 formed by the inner and outer surfaces of thespoiler may simultaneously form a spiral shape. The inner surfaces ofthe more than two spoilers may be planar surfaces, and the outersurfaces thereof may be arc surfaces. The formed hollow rotatingcylinder 702 and the hollow rotating conical cylinder 703 generate apressure difference due to different flow velocities on the inner andouter surfaces of the spoiler during the rotation, thereby betterthrowing the fluid in the hollow rotating cylinder 702 and the hollowrotating conical cylinder 703 to the surrounding. The spoilers may be aplurality of arc lines or straight lines, which form the hollow rotatingcylinder 702 or the hollow rotating conical cylinder 703 of differentgeometric shapes when rotating. For ease of understanding, the hollowrotating cylinder 702 and the hollow rotating conical cylinder 703 mayalso be, for example, a porous rotating cylinder. The difference lies inthat during the rotation, the outer or inner surface of the hollowrotating cylinder 702 and the hollow rotating conical cylinder 703 formsa spiral shape. The path which the fluid in the hollow rotating cylinder702 and the hollow rotating conical cylinder 703 flows through ispreferably a spiral shape, which may also be formed in cooperation witha multi-section concave-convex shape outer or inner surface of thespoiler. In conclusion, the longer the path extended by the hollowrotating cylinder 702 and the hollow rotating conical cylinder 703during the rotation, the more sufficient the combustion of the fuel.

In this embodiment, the hollow rotating cylinder may be implemented incooperation with Embodiments 1 to 5. The supercharging device accordingto the present invention improves the pressure generated by thecompressor and the turbine. Additionally, the hollow rotating cylinderenables sufficient combustion of the fuel in the combustion chamber.Therefore, in this case, the propelling force of the engine issignificantly improved. The hollow rotating cylinder may also bearranged at the rear portion of the compressor and/or the turbine of atraditional engine.

According to this embodiment, the propelling force may be increased evenwith no power device being arranged in the combustion chamber.

In another embodiment, the combustion chamber 4 and the turbine 5 areremoved. The hollow rotating cylinder 702 has a higher rotation velocityover at least one stage of compressor 3 arranged at the rear portion,and the fluid flows through a longer spiral-shape path around the hollowrotating cylinder. Therefore, the flow velocity is even higher, suchthat the compressor generates a pressure difference between the frontand rear portions of the hollow rotating cylinder due to different flowvelocities. The pressure difference is a source of the propelling force.This structure improves the propelling force of the power devices ofvarious compressors with housings or without housings.

Similarly, the combustion chamber 3 and the compressor 3 are removed.The hollow rotating cylinder 702 has a higher rotation velocity over atleast one stage of turbine 5 arranged at the rear portion, and the fluidflows through a longer path. Therefore, the flow velocity is evenhigher, such that the compressor generates a pressure difference betweenthe front and rear portions due to different flow velocities. Thisstructure improves the propelling force of the power devices of variouscompressors with housings or without housings.

It should be understood that the above embodiments are described onlyfor illustrating the present invention, rather than for limiting thepresent invention. A person skilled in the art may make variations tothe above embodiments according to the inventive concept of the presentinvention.

What is claimed is:
 1. A fluid supercharging device, comprising: arotating shaft for rotating under action of a driving force; at leastone stage of an impeller coaxially fixed to the rotating shaft; aplurality of fan blades fixed around a perimeter of each of the at leastone stage of the impeller; wherein a side of each of the plurality ofthe fan blades facing toward fluid is a windward side and another sideof each of the plurality of the fan blades backing on to the fluid is aleeward side, a plurality of fluid guiding inlets are arranged atseveral locations along a lengthwise direction extending from theimpeller to a tip end of the leeward side of each of the plurality ofthe fan blades, and a fluid channel communicating with the plurality ofthe fluid guiding inlets is provided along the lengthwise directioninside each of the plurality of the fan blades; wherein fluidsupercharging device further comprises a suction motor, a suction portof the suction motor is in communication with the fluid channel; whereinwhen the plurality of the fan blades rotate, the fluid flows into thefluid channel via the plurality of the fluid guiding inlets on theleeward side, and the suction motor is configured to generate a suctionforce to enable the suction port to extract the fluid from the fluidchannel to accelerate a flow velocity of the fluid in the fluid channel;wherein a length of each of the plurality of the fan blades is greaterthan that a width thereof, a path where the fluid flows through theplurality of the fluid guiding inlets and the fluid channel in thelengthwise direction of each of the plurality of the fan blades insequence is larger than a path where the fluid flows through the widthof each of the plurality of the fan blades, the fluid flows alongdifferent paths between the windward side and the leeward side of eachof the plurality of the fan blades to generate a pressure difference; atthe same time, the fluid in the fluid channel is extracted out by thesuction motor so that the fluid flows along different paths between thewindward side and the leeward side of each of the plurality of the fanblades in different flow velocities to generate another pressuredifference; the plurality of the fan blades on different stages of theat least one stage transfer backward the pressure differences thereof indescending order in a direction of flow so as to generate a flowpressure within the engine.
 2. The fluid supercharging device accordingto claim 1, wherein the pressure difference between the different stagesof the at least one stage of the plurality of the fan blades arecontrolled by arranging the plurality of the fluid guiding inlets ofdifferent quantities and shapes on the different stages of the at leastone stage of the plurality of the fan blades.
 3. The fluid superchargingdevice according to claim 2, wherein the number and size of theplurality of fluid guiding inlets of each of the plurality of the fanblades decreases progressively along the lengthwise direction distalfrom the impeller.
 4. The fluid supercharging device according to claim1, wherein the rotating shaft is internally provided with a rotatingshaft inner channel; the fluid supercharging device further comprises asuction pipe positioned in the fluid channel, wherein the suction pipeis configured to communicate with the suction port and the suction motor, and the suction port communicating with the suction pipe is positionedat an end of each of the plurality of the fan blades distal from theimpeller within the fluid channel, and in communication with the fluidchannel, and the suction pipe extends along the lengthwise direction ofeach of the plurality of the fan blades and is in communication with therotating shaft inner channel, and is in communication with the suctionport of the suction motor via the rotating shaft inner channel.
 5. Thefluid supercharging device according to claim 1, wherein the fluidchannel is internally partitioned by an isolation layer into a firstchannel in communication with the fluid guiding inlet and a secondchannel in communication with the suction port of the suction motor, thefirst channel and the second channel are positioned in the fluidchannel, and the first channel is in communication with the secondchannel via the suction port at the end of each of the plurality of thefan blades distal from the impeller.
 6. The fluid supercharging deviceaccording to claim 5, wherein at least one of an inner wall of the fluidchannel and a surface of the isolation layer provides a spoiler facealong a long fluid flowing path.
 7. The fluid supercharging deviceaccording to claim 6, wherein a shape of the spoiler face is aconcave-convex streamline shape, a wave shape, or an arc shape.
 8. Thefluid supercharging device according to claim 1, wherein the suctionmotor is coaxially arranged with the rotating shaft, a rotation velocityof the suction motor is greater than that of the rotating shaft; or thesuction motor is arranged outside a working area of the fan blades. 9.The fluid supercharging device according to claim 1, wherein the atleast one stage of the impeller comprises a plurality of stages ofimpellers, the stages of the impellers being sequentially arrangedcoaxially, the fan blades fixed on each stage of the plurality of stagesof the impellers employing the supercharging device, or the fan bladesfixed on a last stage of the plurality of stages of the impellers distalfrom a fluid intake direction employing the supercharging device. 10.The fluid supercharging device according to claim 1, wherein a centralline of an opening-shape of each of the plurality of fluid guidinginlets is consistent with a rotation direction and angle of each of theplurality of the fan blades.
 11. The fluid supercharging deviceaccording to claim 1, wherein the plurality of the fan blades coupled toa perimeter of the at least one stage of the impeller employ the fluidsupercharging device, under action of the driving force, the fan bladesgenerate the pressure difference between the windward side and theleeward side under driving of power or driving of an external force,wherein the driving force comprising at least one of the power and theexternal force.
 12. The fluid supercharging device according to claim11, wherein the external force comprises at least one of a wind force, ahydraulic force, and a stream force capable of driving the fan blades torotate.
 13. The fluid supercharging device according to claim 10,wherein the opening-shape comprises at least one of a circle shape, anelongated shape, a rhombus shape, an ellipse shape, and an arc shape.14. The fluid supercharging device according to claim 10, wherein theopening-shape of the plurality of guiding inlets which are arrangedalong the lengthwise direction of each of the plurality of the fanblades are different.
 15. The fluid supercharging device according toclaim 1, wherein the suction port of the suction motor is incommunication with the fluid channel via the plurality of the fluidguiding inlets, and a gas outtake of the suction motor is communicatedwith outside.
 16. The fluid supercharging device according to claim 1,wherein the suction port of the suction motor is in communication withthe fluid channel via the plurality of the fluid guiding inlets, and agas outtake of the suction motor is communicated with a gas intakepassage of the fluid supercharging device via a pipeline.
 17. The fluidsupercharging device according to claim 4, wherein the suction pipe is athreaded pipe or a spiral pipe.